Composite space vehicle



2 Sheets-Sheet l File' March A 1ginal Oct. 8, 1968 N E w ,w m m c i E nw w i. d w v n o n l n w m n 4 i, M 5 n m Maa @Tuk s. w a n H d6 v w .4.1T :k w 2 0? e. uw 3 n .M 8 uw \l 3 m 2 w v un m 3 1.1 3 I n -Ilff n f 1//////////////////////////////d u m u maf, W ATTORNEYS Oct. 8, 1968 L A.COHEN COMPOSITE SPACE VEHICLE 2 Sheets-Sheet 2 Jriginal Filed March E,1963 FIG. 4.

ATTORNEYS United States Patent O 26,475 COMPOSITE SPACE VEHICLE LeonardA. Cohen, 224 Old Lancaster Road, Mei'ion Station, Pa. 19066 originalNo. 3,173,627, dared Mar. 16, 196s, ser. No.

263,818, Mar. 8, 1963. Application for reissue Mar. 14,

1967, Ser. No. 626,648

8 Claims. (Cl. 244-1) Matter enclosed in heavy brackets appears in theoriginal patent but forms no part of this reissue specilication; matterprinted in italics indicates the additions made by reissue.

ABSTRACT F THE DISCLOSURE Apparatus including support means for y'xedlyand firm- Iy supporting a human thereon, means for moving said apparatusso as to cause a predetermined force to be imparted by the support meansupon the human, and means for imparting rotational movement to saidsupport means and human thereon about an axis perpendicular to thedirection of said force and which axis substantially coincides with thelongitudinal axis of a human fixed on the support so as to import acontinuing change in the direction of the force with respect to thehuman.

The present invention relates to an improved vehicle system for use inspace exploration and, more particularly, this invention relates to avehicle configuration wherein excursions may be made from the primaryspace craft without destroying the structural integrity of the primaryvehicle. In addition, the present invention relates to a space vehiclesystem which is particularly designed so as to be compatible with meansfor substantially increasing the ability of personnel within the vehicleto withstand greatly increased forces of acceleration and decelerationas well as the large gravitational forces encountered inthe explorationof celestial bodies having several times the gravitational force ofearth.

Referring rst to the design of the space vehicle, previous vehicles haverelied upon tandem arrangements of separable propulsion and mannedsections. As a result of this tandem arrangement, the presently designedvehicles for use in future exploration of the moon, as well as othercelestial bodies, require that at least two sections be disengaged fromone another in order to launch the manned sections and, in someinstances, require that the sections be recoupled in space for thereturn to earth. Furthermore, some tandem arrangements require that oneor more of :the sections be rotated end for end before launching themanned section or before being recoupled to the propulsion section forthe return trip. In addition, such tandem arrangements make it necessaryto place the astronaut within the manned section or capsule while thelatter is positioned on top of a multiple stage propulsion section. Thisinvolves the necessity of retaining the astronaut within the crampedconditions for extended periods of time during the elaborate count-downprocedures required for the launching vehicle which can only beaccomplished subsequent to the joinder of the manned and propulsionsections.

It is therefore a primary object of the present invention to provide aspace vehicle system wherein the above mentioned problems of the tandemarrangement are entirely or substantially avoided.

In addition, it is another primary object of the present invention toprovide a space vehicle system which is specifically designated so `asto faciiltate the use of means for rotating the personnel within thevehicle during periods of extreme acceleration or deceleration wherebyRe. 26,475 Reissued Oct. 8, 1968 substantially greater forces may betolerated for greatly extended periods of time. For example, presentstudies indicate that the degree of gravitational, acceleration ordeceleration forces which may be tolerated by a human being varyinversely with respect to the length of time during which such forcesare present. That is, although a force of 6 g may be sustained for aperiod of one minute, a force of no more than 3 g may be sustained for aperiod of three minutes. The physiological reason for this is that theviscosity of the blood and the relatively large mass of the elasticallysuspended internal organs present a large amount of inertia which mustbe overcome by the above indicated forces before damage such ashemorrhaging or other serious etiects occur. Thus, the present inventionrecognizes and effectively utilizes these physiological facts byrotating the astronaut about an axis transverse to the direction of theimpinging force so that the effective direction of the force on theblood and internal organs is constantly changed thereby substantiallylessening the destructive effect of these forces.

The above objects las well as other more particularly relating to thedetails of construction and resultant advantages will become more fullyapparent from the following description when taken in conjunction withthe accompanying drawings in which:

FIGURE 1 is an elevational, plan view of a vehicle system designed inaccordance with the principles of the invention, the lower portion ofthe vehicle system being broken in order to reduce the size of thefigure;

FIGURE 2 is a partly sectional view showing an enlarged portion of thevehicle system;

FIGURE 3 is a sectional view taken along the plane indicated by the line3-3 of FIGURE 2;

FIGURE 4 is a sectional view of a space vehicle in combination with aFirst form of rotary mechanism for enabling the astronaut to toleratesubstantially increased acceleration and deceleration forces; and

FIGURE 5 is a sectional view of a portion of the space vehicle systemshown in FIGURE 2 in combination with an alternative form of rotarymechanism.

Reference is now made to FIGURE l which illustrates a preferred form ofspace vehicle system in accordance with the principles of the presentinvention. This vehicle system includes a booster propulsion section 10and a nal stage vehicle 12 the latter of which includes a selfcontainingpropellent section 14 and a plurality of moveable nozzles 16. Theorientation of nozzles 16 may be varied by pneumatic or hydraulic motors18 actuated by solenoid operated valves 19 so that the direction ofvehicle flight may be varied. Of course, it is to be understood that thebooster stage 10 may comprise a plurality of separable stages as ispresently well known in the art.

The final stage vehicle 12, hereinafter referred to as the motorvehicle, is provided with a sliding cover plate 20 the peripheral edgeof which is secured in longitudinally extending guides 22 as shown mostclearly in FIGURE 2.

Cover 20 is preferably of circular contiguration and is capable oflongitudinal movement between the solid line and the dotted linepositions shown in FIGURE 1 under the operation of a pneumatic orhydraulic motor 24 connected thereto by a connecting link 26, motor 24being controlled by a solenoid operated valve 27.

Referring now to FIGURES 2 and 3, the mother vehicle 12 includes anouter shell 28 within which there is secured a support structure 30 thelatter of which denes a conical well in axial `alignment with anaperture 32 provided in shell 28. Thus, upon operation of motor 24,hatch 20 may be moved to the dotted line position shown in FIGURE 1 sothat access may be gained to the interior of the well formed by thesupport structure 30.

Support structure 30 is of sufcient size so as to accommodate andsupport a second vehicle 34 hereinafter referred to as the excurisionaryvehicle. Although the excursionary vehicle may be of variousconfigurations, it is illustrated as being cylindrical for purposes ofthe present description. Vehicle 34 is supported within the mothervehicle 12 by means of a plurality of extendible legs 36 located in setsof four at opposite longitudinal ends of the vehicle. Each of legs 36may be extended and retracted by an associated, double acting, hydraulicor pneumatic motor 38 under the control of a solenoid operated controlvalve 39. The exterior end of each of legs 36 mounts a ball bearing 4I)which, when the leg is extended as shown, is received within asemi-spherical cavity 42 provided in the internal surface of supportstructure 30. Thus, legs 36 and cavities 42 cooperate to form adisengageable supporting and locking arrangement whereby theexcursionary vehicle may be securely locked in position within themother vehicle, the legs being tirst retracted when the excursionaryvehicle is about to leave or enter the well of the mother ship.

As further shown in FIGURES 2 and 3, the excursionary vehicle includes apair of external nozzle assemblies 44 positioned on diametricallyopposed sides of the vehicle. Each of these assemblies includes fournozzles 45a-d which are fixed and orientated at 90 with respect to eachother. Each of these nozzles is connected to a central supply conduit 46through which a suitable propulsion tiuid is supplied to the individualnozzles from a source (not shown) contained within the excursionaryvehicle. The nozzle assemblies further include individual valves 48a-dwhich permit individual regulation of each of the nozzles whereby theorientation and the direction of propulsion of the excursionary vehiclemay be controlled by the astronaut located therein.

In addition to effecting control of the excursionary vehicle per se, thepresent invention further contemplates the control of the mother vehicleby the astronaut located within the excursionary vehicle although it isto be understood that additional astronauts may also be carried by themother vehicle and exert control over the operation thereof. In order topermit the astronaut within the excursionary vehicle to control thetrajectory and attitude ot: the mother vehicle, an electricalinterlocking system S is provided between suitable controls located inthe excursionary vehicle and the solenoid valves 19 which control theoperation of the nozzles 16. This system includes a pneumatic orhydraulic motor 52 positioned at the right-hand end of the excursionaryvehicle as viewed in FIGURE 2. A control valve 53 controls the admissionand exhausting of motive fluid so as to extend or retract rod 54 whichcarries a head 56 having a plurality of male plugs 58. The plugs areadapted to be received within female receptacles provided in member 59when the head 56 is extended, electrical interconnection between thecontrols within the excursionary vehicle and plugs 58 being accomplishedthrough a ilexible cable 60. Of course, it is to be understood that theplurality of electrical channels provided by plugs 58 are connectedthrough cable 61 to the solenoid valve 27 controlling motor 24 as wellas to valves 19 controlling the operation of motors 18.

Lasty, a plurality of visual ports 64 and a hatch 68 containing anadditional port 66 are provided in one end of the excursionary vehicleas shown in FIGURE 3 and it is to be understood that additional portsare also provided in the opposite end of the vehicle. A hatch 35 is alsoprovided in the circumferential wall of the excursionary vehicle andhatches 31 and 33 are provided in well structure 30. Thus, the astronautmay leave the excursionary vehicle and effect inspection and/or repairof the mother vehicle if such becomes necessary during ight.

The operation of the vehicle system will be apparent from the precedingdescription. When the mother vehicle has reached a predeterminedlocation such as an orbital path about the moon or a planet, theastronaut first opens hatch 20 by energizing solenoid valve 27 so as toactuate motor 24, solenoid valve 27 being operatively connected to thecontrols within the excursionary vehicle through the electricalinterconnection provided by system 50. Once the hatch is open, theastronaut may then actuate the valves associated with motors 52 and 38so as to retract plugs 58 and legs 36, whereupon, the excursionaryvehicle becomes detached from the mother vehicle and may then departtherefrom under the propulsion provided by nozzle assemblies 44 and theassociated propellent system. Conversely, when the excursionary vehiclereturns to the mother vehicle, ball bearings 40 guide the entrance ofthe vehicle into the well and, after the vehicle is properly orientated,legs 36 are fully extended into pockets 42. Thereafter, electricalconnection is again established by the extension of head 56 and theplugs S8 into the receiving connectors. Thus, with communication againestablished with the mother vehicle, the hatch 20 may be closed and thetrajectory of the mother vehicle may then be controlled by the suitableorientation of nozzles 16 since motors 18 are also under the control ofthe astronaut through the electrical connection 50.

Turning now to the aspects of the invention relating to the reduction ofthe effects of acceleration and deceleration forces on the astronaut,reference is made to FIGURE 4 which illustrates the principles of thepresent invention as employed in combination with a space vehicle of anyconliguration, the outer walls of the vehicle being indicated at 70. Forexample, the configuration of the space vehicle may be that of thepresently designed Mercury or Apollo capsules as well as that of otherproposed systems such as the Dyna-soar Space Glider or other futurevehicles of different conguration.

In the illustrated example, walls 70 of the vehicles are shown to betapered at 72 and it is to be understood that the tapered portionindicates the forward or leading portion of the vehicle when it is inliight. That is, the direction of the vehicles velocity is indicated byarrow V. It will therefore b apparent that the effect of vehicleacceleration on the astronaut results in a force acting in the directionof arrow A, whereas, deceleration of the vehicle results in a forceacting on the astronaut in the direction of arrow D. Thus, the presentinvention contemplates the rotation of the astronaut about an axisindicated by line c-c which is perpendicular to the direction ofvelocity as well as the directions of the acceleration and decelerationforces. As a result of rotation about this axis, the blood and internalorgans of the astronaut will be subjected to a displacing force in aglven direction for only a brief interval of time and, since theastronaut is rotated through a full 360, the net result of the forceswill be zero for each revolution. It will therefore be apparent thatneither the blood nor the internal organs will be greatly displaced inany given direction which might prove to be harmful, but rather, theblood and internal organs will tend to oscillate only slight amounts ineach direction as the astronaut is rotated. Insofar as the rate ofrotation is concerned, the optimum angular velocity of rotation of theastronaut is dependent upon the magnitude of the acceleration anddeceleration forces which, in turn, are dependent upon the maximum oroptimum values from the standpoint of rocket efficiency and the distancewhich is to be traversed by the space vehicle. Of course, the maximumangular velocity of rotation must be maintained at a value which willnot cause undesirable centrifugal forces to adversely effect theastronauts circulatory system or the other internal organs. For example,it is desirable that the maximum magnitude of centrifugal force be lessthan the force of gravity on earth so as to insure maximum comfort forthe astronaut.

In the form of the invention shown in FIGURE 4, the rotary mechanismincludes a rigid frame member 74 having a rst portion 76 which carries acontrol panel 78,

the latter preferably extending circumferentially about the astronautfor approximately 180. Frame member 74 further includes a second,integral portion 80 which surrounds the astronaut on three sides and towhich is secured a removable liner 82 the latter of which is contouredto t the requirements of an individual astronaut. The astronaut issecured in the horizontal position by means of a plurality of straps 84,86 and 88 as well as a helmet lock 90 secured to frame member 74. Thestraps are preferably secured to the frame portion 80 by removable clipsso that, during periods of non-acceleration or deceleration, theastronaut may uncouple the straps and unlock the helmet lock 90 so as toleave the contoured seat and move about the space craft if there issufficient room therein for this purpose.

The entire astronaut support structure and control panel is `mounted forrotation about axis c-c by means of a pair of shafts 92 and 94 rigidlysecured to opposite ends of frame 74. Shaft 92 is journalled in a radialand axial thrust bearing indicated at 96 which is secured to the vehicleiwall 70. Shaft 94 is connected to a conventional motor and brake unit98 so that the entire assembly may be rotated during periods ofacceleration or deceleration and secured against rotation during periodsof non-acceleration or deceleration.

In order to permit the astronaut to control various functions of thespace vehicle such as the orientation of propellent nozzles, the variouscontrol switches, two of which are shown at 63 and 65, are connectedthrough electrical leads 100 and cable 102 to a 'wiper arm 104 carryinga plurality of contacts 106. Contacts 106 frictionally engage aplurality of slip rings 108 secured in a stator member 110 secured tothe vehicle wall 70. 0f course, it is to be understood that the variouscommunication channels provided by contacts 106 are electricallyconnected to suitable control mechanisms such as valves 19 or 48 forcontrolling the attitude and trajectory of the space vehicle the latterof which may be either a mother vehicle such as vehicle 12 or anexcursionary vehicle such as 34.

Reference is now made to FIGURE 5 which illustrates a preferredembodiment of the `present invention which incorporates the advantagesof the lateral access vehicle system described with regard to FIGURES1-3 as well as the advantages of the rotating system just described.Those elements shown in FIGURE 5 which are identical to previouslydescribed elements of FIGURES 1-3 are correspondingly numbered and,include the mother vehicle 12 having a sliding hatch 20 which permitsthe entrance and departure of the excursionary vehicle 34, hatch 20including a visual lport 21 aligned with port 66. Vehicle 34 furtherincludes the previously described retractable legs 36 having bearings40, however, it is to be noted that the previously described pockets 42are replaced by annular grooves 112 so that the entire excursionaryvehicle is capable of rotation about the axis c'-c'. Since the entirevehicle 34 is adapted to rotate as a unit, frame 74 is merely secured tothe vehicle wall so as to rotate therewith, the rotation being suppliedby motor 114 which is coupled to the excursionary vehicle by means of anaxially separable clutch 116.

In order to maintain electrical communication between the excursionaryvehicle and the mother vehicle when the two are in the assembledcondition illustrated in FIG- URE 5, a pair of hydraulic or pneumaticmotors 118 are provided so as to reciprocate an annular member 120carrying a plurality of male connectors as described with reference tothe FIGURE 2 embodiment. However, since the excursionary vehicle is torotate with respect to the mother vehicle, the aforementioned contactsare adapted to be received in an annular ring 122 which is rotatablyconnected to a stator ring 124, such slip rings being well known in theart. Of course, it is to be understood that stator ring 124 iselectrically connected through suitable leads to the valves controllingmotors 18 and 24 as shown in FIGURE 1 while ring 120 is electricallyconnected to 6 the control switches 63 and 65' contained on panel 126through cable 127 and flexible conduit 128. It will also be understoodthat the vehicle is provided with all of the necessary life supportingequipment and the necessary propulsion lluid source all of which may belocated within chamber 130.

From the foregoing description of the structural elements it will beapparent that the present invention provides a vehicle system whereinthe excursionary vehicle may function in a dual capacity. That is, itmay function as a separate vehicle capable of excursions independentlyof the mother vehicle as, for instance, in landings or closesurveillance of a celestial body while the mother vehicle remains inorbit thereabout. At the same time, the excursionary vehicle is capableof becoming a functional and operative control center for the operationof the mother vehicle due to the electrical coupling assembliesdescribed hereinabove. Furthermore, and most importantly, theconfiguration of both vehicles is specifically designed so as to securethe substantial increase of rocket efficiency due to the fact that theastronaut may be rotated in the above described manner so as to greatlyreduce the serious physiological effects of prolonged periods ofacceleration and deceleration. Thus, the present invention whileericompassing features which may be used independently of each other, isspecifically designed so that all of the desirable features may becombined to form the preferred embodiment illustrated in FIGURE 5.

It will also be noted that the lateral access arrangement permits theexcursionary vehicle to be ejected from the mother ship during any stageof flight as well as in the event of an abortive launching of thesystem. In addition it will be readily apparent that the astronaut andthe various systems contained within the excursionary vehicle may bemore thoroughly and rapidly checked out in a laboratory entirely apartfrom the mother vehicle prior to the placement of the excursionaryvehicle in the latter.

Of course, numerous changes and modications may be made withoutdeparting from the scope of the invention. For example, electric motorsmay be readily substituted for motors 24, 38, 52 and 118 so that theassociated control valves may be eliminated. Of course, it is to beunderstood that the electrical interconnection provided by system 50 isalso capable of interconnecting the control panel in ythe excursionaryvehicle with the various known indicators commonly provided for thepurpose of indicating the pressure, temperature and fuel conditions ofthe mother vehicle. Furthermore, it will be readily apparent that anynumber of astronauts may be rotated in the above described manner eitherabout independent axes or axially spaced along the same axis.Alternatively, a plurality of astronauts may be positioned in aback-to-back relationship with the axis of rotation passingtherebetween. ['Thus, it is to be understood that the foregoingdescription is intended to be merely illustrative of the principles ofthe present invention and that numerous changes and modications may bemade therein without departing from the scope of claims as hereinafterset forth] What is claimed is:

1. A space vehicle system comprising a mother vehicle and anexcursionary vehicle, said mother vehicle including a forward section, amid section and an aft section, propulsion means 'positioned in said aftsection, a well located in said mid section opening to the exterior ofsaid vehicle, said excursionary vehicle being of a size so as to bereceived within said well so as to be carried by said mother vehicle,said excursionary vehicle including self-contained propulsion means forpropelling said excursionary vehicle out of and independently of saidmother vehicle, control means within said excursionary vehicle foroperating said mother vehicle propulsion means, separable connectormeans for connecting said control means with said mother vehiclepropulsion means when said excursionary vehicle is within said well,means for rotatably supporting said excursionary vehicle within saidmother vehicle, and means for rotating said excursionary vehiclerelative to said mother vehicle about an axis penpendicular to thedirection of flight of said mother vehicle.

2. A space vehicle system comprising a mother vehicle and anexcursionary vehicle constructed to be carried by said mother vehicleand for independent excursionary flights from and return to said mothervehicle, said mother vehicle including a forward section, a mid sectionand an aft section, propulsion means positioned in said aft section, awell located in said mid section opening to the exterior of saidvehicle, means dening an opening in the side of said mid sectionproviding a passage for lateral movement of said excursionary vehiclebetween said well and the exterior of said mother vehicle, saidexcursionary vehicle being of a size so as to be received within saidwell and carried by said mother vehicle therein, said excursionaryvehicle including self-contained propulsion means for propelling saidexcursionary vehicle out of and independently of said mother vehicle forexcursionary trips and return to said mother vehicle, control meanswithin said excursionary vehicle for operating said mother vehiclepropulsion means and separable connector means for connecting saidcontrol means with said mother vehicle propulsion means when saidexcursionary vehicle is within said well.

3. A space vehicle system as claimed in claim 2 comprising meansoperable from within said excursionary vehicle for connecting anddisconnecting said connector means, and hatch means for covering saidopening, said hatch means being movable to uncover said opening.

4. A space system as claimed in claim 2 wherein said connector meanscomprises electrical connectors.

5. A space vehicle having propulsion means for accelerating said vehiclein a given direction, means for supporting an astronaut within saidvehicle, means for rotating said supporting means and said astronautabout an axis perpendicular to the direction of said acceleration so asto constantly change the direction of acceleration forces with respectto the internal organs of said astronaut, control means connected tosaid propulsion means for controlling the trajectory of said vehicle,and means for rotating said control means about said axis at a rate ofrotation equal to that of said astronaut.

6. A space vehicle system comprising a vehicle, propulsion means forproviding acceleration to said vehicle in a given direction, means forsupporting an astronaut on said vehicle, means for rotating saidsupporting means pendicular to the direction of said acceleration so asto and said astronaut supported thereby about an axis perchangeconstantly the direction of acceleration forces with respect to theinternal organs of said astronaut, and control means for effectingcontrol over flight conditions of the vehicle system, said control meansbeing mounted on said supporting means for rotation therewith and foraccess to said astronaut during rotation of said supporting means.

7. In combination, a rst space vehicle, a second space vehicle removablycontaining said first vehicle, said second space vehicle havingpropulsion means for accelerating the same in a given direction, meansfor supporting an astronaut within said rst vehicle, and rotating meansconnected between said first and second vehicles so as to rotate saidfirst vehicle, said support means and said astronaut relative to saidsecond vehicle about an axis perpendicular to the direction of saidacceleration so as to change constantly the direction of accelerationwith respect to the internal organs of said astronaut.

8. Apparatus including support means for fxedly and firmly supporting ahuman thereon comprising a rigid support member and means for clamp-ingthe human with respect to the rigid support member 'for movementtherewith, means for moving said apparatus so as to cause apredetermined force to be imparted by the support means upon the human,and means for imparting rotational movement to said support means andhuman thereon about an axis perpendicular to the direction of said forceand which axis .substantially coincides with the longitudinal axis of ahuman fixed on the support so as to impart a continuing change in thedirection of the force with respect to the human.

References Cited The f ollowing references, cited by the Examiner, areof record in the patented tile of this patent or the original patent.

UNITED STATES PATENTS 2,399,217 4/1946 Fahrney 244-2 2,985,413 5/19'61Widmanstetter 244-140 3,010,219 ll/l961 Schueller 35-12 3,053,576 9/1962Mohar 244-1 3,073,040 1/1963 Schueller 244-1 2,534,471 12/1950 Norheim128-24 X FERGUS S. MIDDLETON, Primary Examiner.

